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WO/2021/037785A1 |
The present disclosure relates to deployable structures, to methods and apparatus for deployment of deployable structures, and to associated manufacturing methods. Such deployable structures suitably comprise components for space structu...
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WO/2021/035757A1 |
Provided is a moon-based environment simulation device (100), comprising a moon ground simulation system (101) and a moon rock simulation system (103) which are arranged in a connection manner, the moon ground simulation system (101) is ...
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WO/2021/037787A1 |
The present disclosure relates to deployable structures, to methods and apparatus for deployment of deployable structures, and to associated manufacturing methods. Such deployable structures suitably comprise components for space structu...
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WO/2021/039652A1 |
A debris removal satellite (300) comprising a capture device (135), a chemically-propelled thruster (341), and a propellant tank (342) that stores chemical fuel. A solar cell paddle (371) can be operated in an orbit having a higher orbit...
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WO/2021/042076A1 |
Systems and methods described herein include collapsible and deployable antenna structures including shape memory composite components.
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WO/2021/037786A1 |
The present disclosure relates to deployable structures, to methods and apparatus for deployment of deployable structures, and to associated manufacturing methods. Such deployable structures suitably comprise components for space structu...
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WO/2021/031686A1 |
A transfer type contra-rotating geomagnetic energy storage-release delivery system and method therefor, the system comprising a control system, a three-axis control moment canceller and an energy system which are arranged on a delivery m...
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WO/2021/031740A1 |
The invention provides a multi-purpose planet rover, relating to the technical field of planet explorations. The multi-purpose planet rover comprises: a container body, wherein first rotating wheels are respectively mounted on left and r...
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WO/2021/026412A1 |
A modular and scalable system to transfer space articles between space orbits. In one embodiment, the system employs a rendezvous vehicle which docks with a space article in an initial orbit, the connected stack then docking with a locom...
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WO/2021/022253A1 |
Systems and methods for controlling satellites are provided. In one example embodiment, a computing system can obtain a request for image data. The request can be associated with a priority for acquiring the image data. The computing sys...
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WO/2021/019827A1 |
Provided is a system for satellite operators by which information relating to retrieved ground stations can be easily obtained. An information processing device according to the present technology is provided with a user interface unit w...
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WO/2021/014137A1 |
A device comprising a first member (12) for supporting a user (200); and a second member (14), attached to the first member (12), comprising a counterbalance portion (16). The first member (12) and the second member (14) are each moveabl...
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WO/2021/012729A1 |
A space launch system and method based on electromagnetic pushing. The space launch system comprises an energy storage subsystem (1), an energy conversion subsystem (2), a linear motor subsystem (3), and a control maintenance subsystem (...
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WO/2021/016040A1 |
A method for providing thermal balance of spacecraft electronics is provided. The spacecraft includes two or more electronic units wherein each electronic unit is capable of performing the same spacecraft operational task. The method for...
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WO/2021/012539A1 |
A low-disturbance dual-gimbal flywheel based on a spatial parallel mechanism, comprising a parallel mechanism platform. The parallel mechanism platform is a spatial parallel mechanism that comprises N drive branches, a stationary base, a...
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WO/2021/014293A1 |
A satellite module (10) for attitude determination comprises a containment body (11) comprising at least one data acquisition board (17) and a connection interface (14), at least one first-type sensor (12) selected from a sun sensor, an ...
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WO/2021/016563A1 |
A display system can be configured to receive, via a user interface, a first identifier associated with a first space object and determine a first maneuver of the first space object. The first maneuver can include a perturbation of the p...
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WO/2021/008063A1 |
A deorbiting sail unfolding method and apparatus thereof. The apparatus comprises an unfoldable sail (200) and a foldable sail (300); the unfoldable sail (200) and the foldable sail (300) are rotatably connected to form a deorbiting sail...
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WO/2021/008603A1 |
Disclosed by the present invention is a multifunctional bionic thermal protection structure formed on the basis of the SLM technology. The multifunctional bionic thermal protection structure comprises surface layers and a functional laye...
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WO/2021/011587A1 |
Disclosed are systems and method for satellite attitude control, which includes two or more individual thruster unit (ITU) arranged at various locations about a body of the satellite, with each ITU oriented to provide thrust in a unique ...
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WO/2021/001945A1 |
The present invention provides a spectroscopic imaging device (1) including: a spectroscopic unit (2) that includes a field diaphragm (2d), a shading optical element (2c), a dispersion element (2f), and a two dimensional detector (2h); a...
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WO/2021/000047A1 |
The present disclosure relates to a low mass system for releasably securing a robotic arm to a spacecraft and also securing various payloads to the robotic arm and to each other, permitting the robotic arm to be both moved from one locat...
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WO/2020/261397A1 |
A device communication apparatus (950) communicates with at least one of a master satellite (310) and a slave satellite (320). A control unit (110) generates a control command (51) that controls the master satellite (310) and the slave s...
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WO/2020/261481A1 |
A satellite constellation (100) is provided with a plurality of artificial satellites (110). The plurality of artificial satellites each travel around an inclined circular orbit multiple times per day. Normal lines to a plurality of orbi...
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WO/2020/260662A1 |
Systems and methods for determining parameters suitable for determining an orbit of a satellite using TDOA parameters and several spaced receivers.
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WO/2020/256024A1 |
A satellite constellation formation system forms a satellite constellation (20) having an N number (N being a natural number) of orbital planes (21) having mutually different normal directions. A satellite constellation formation unit fo...
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WO/2020/255310A1 |
A satellite constellation formation system forms a satellite constellation (20) having an N number (N being a natural number) of orbital planes (21) having mutually different normal directions. A satellite constellation formation unit fo...
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WO/2020/256792A1 |
A structure for changing the attitude of a spacecraft is provided including an elongated member and a plurality of actuators coupled to the elongated member. The elongated member is coupled to the spacecraft. The elongated member has a l...
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WO/2020/257649A1 |
Various embodiments of a vortex thruster system is described herein that is configured to create at least three discrete thrust levels. In some embodiments, the vortex thruster system is configured to decompose a monopropellant and deliv...
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WO/2020/250131A2 |
The present invention relates to a tank for containing a component fluid or a mixture of components.
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WO/2020/250709A1 |
The present technology relates to an artificial satellite and a control method for the same that can reduce battery consumption and guarantee the quality of captured images. An artificial satellite is provided with an image capturing dev...
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WO/2020/250706A1 |
The present technology pertains to: an image processing method enabling image processing on a plurality of captured images obtained through operation of formation flight; and a metadata data structure. In the present technology, an image...
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WO/2020/250708A1 |
The present technology pertains to: an image management method enabling management of an image captured by an artificial satellite; and a metadata data structure. In the present technology, a management device for managing an image captu...
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WO/2020/249987A1 |
The subject of the present invention relates to a floating platform (10) for launching a space rocket (100) from high altitude comprising a support structure (20) for suspending the space rocket (100) and which support structure (20) can...
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WO/2020/249831A1 |
Multiple hold-down and release device (1) for spacecraft, that comprises: - a central structure (2) comprising: - a central section (3) with an inner hole (4) with a cylindrical surface comprising an end stop (5), an inner axial shaft (6...
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WO/2020/250707A1 |
The present invention pertains to: a satellite system imaging method which, in satellite remote sensing, enables an artificial satellite to capture an image in response to an event that has taken place on the ground; and a transmitting d...
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WO/2020/245897A1 |
A landing gear (100) comprises a leg (110A, 110B, 110C), a rotating body (130A, 130B, 130C), and a housing (150). The leg (110A, 110B, 110C) makes contact with the landing surface at one end and moves linearly in the axial direction with...
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WO/2020/245549A1 |
A space aircraft (1) comprises a fuselage (3), two wings (4A, 4B) arranged on either side of the fuselage (3), and two nacelles (7A, 7B) arranged at the ends of the wings (4A, 4B) and each carrying a horizontal tail (8A, 8B) and a vertic...
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WO/2020/246951A1 |
A reconfigurable power processing unit for a spacecraft including a plurality of power modules. Each of the power modules includes a first power source and a second power source. The first power source and the second power source are con...
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WO/2020/246168A1 |
This method for estimating a right-under point position of an on-orbit object comprises: a photographing step for photographing an observation image of the on-orbit object (X) together with a known object of which orbit is known; a first...
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WO/2020/245193A1 |
The invention relates to a method and a system for determining the capability of a sensor contained in a satellite to access a target region (8). The position (5) of the satellite is ascertained, the viewing radius of the sensor in the d...
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WO/2020/240826A1 |
A satellite constellation formation system in which each satellite in an orbit satellite group is provided with a propulsion device for changing the speed of each satellite in the orbit satellite group. A satellite constellation formatio...
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WO/2020/240824A1 |
This satellite constellation formation system forms a satellite constellation (20) including a plurality of orbital planes (21), each having a plurality of satellites flying at the same orbital height. A satellite constellation formation...
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WO/2020/242477A1 |
Propulsion systems, such as electro spray thrusters, may include an electrically actuated valve to permit a selective flow of propellant to a thruster. The valve may be located and arranged such that it physically separates a propellant,...
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WO/2020/240825A1 |
A satellite constellation formation system forms a satellite constellation (20) that includes two orbital planes which have differing normal-line orientations and in which the same number of satellites travel. A satellite constellation f...
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WO/2020/236961A1 |
An electrospray apparatus including a plurality of emitters, disposed on a substrate, wherein the plurality of emitters can have a narrow parameter distribution, and where the apparatus can optionally include one or more control systems,...
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WO/2020/236256A1 |
A space optical system is disclosed. The space optical system (100) includes a primary support structure (110) in support of a primary mirror (111). The space optical system also includes a sensor mounting structure (101) coupled to the ...
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WO/2020/234529A1 |
The present description relates to a device (7) for recognising the attitude of an object, characterized in that it comprises: a sphere (11) comprising a wall (13) able to let a light flux at least partially pass; a ball (17), moveably m...
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WO/2020/234540A1 |
Space launcher comprising a launcher body (1), an engine (2), a combustion chamber (4), a nozzle (5) having a main axis (Z-Z), the nozzle (5) being provided with a plate (6) extending radially, the plate (6) having an inner face and an o...
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WO/2020/234539A1 |
Space launcher comprising a launcher body (1), an engine (2), a nozzle (5) provided with a plate (6) extending radially around the nozzle (5) or a combustion chamber (4) and insulating an internal volume of the spacecraft from an externa...
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